US2024009806A1PendingUtilityA1
Thrust reduction system for a blast nozzle
Est. expiryDec 2, 2040(~14.4 yrs left)· nominal 20-yr term from priority
Inventors:Matthew David Campbell RowlandTrevor Andrew SeewaldIngo Johannes Henri JahnPhillip Bradley Swann
B24C 5/04B05B 7/1486B05B 1/005B05B 15/65
26
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Claims
Abstract
A blast nozzle thrust reduction blasting system comprising:a source of blasting gas in a predetermined pressure range with abrasive particles entrained therein;a nozzle includinga nozzle inlet for connection to the source of blasting gas,a nozzle outlet for emission of the blasting gas,a nozzle conduit from the nozzle inlet to the nozzle outlet including a throat therebetween with a ratio of area of the nozzle outlet to area of the throat selected to emit the blasting gas from the nozzle outlet to produce a supersonic jet;a thrust reducer connectable to the nozzle, to receive the supersonic jet exiting the nozzle, the thrust reducer comprising a body with a thrust reducer conduit therethrough, the body being of sufficient length and diameter to cause a flow condition of the jet received from the nozzle outlet to be modified such that a zone of sub-atmospheric pressure forms adjacent a face of the outlet of the nozzle whereby a pressure differential arises between the zone of sub-atmospheric pressure and surrounding atmosphere thereby creating an anti-thrust force in opposition to thrust of the nozzle.
Claims
exact text as granted — not AI-modified1 . A blast nozzle thrust reduction blasting system comprising:
a source of blasting gas in a predetermined pressure range with abrasive particles entrained therein; a nozzle including
a nozzle inlet for connection to the source of blasting gas,
a nozzle outlet for emission of the blasting gas,
a nozzle conduit from the nozzle inlet to the nozzle outlet including a throat therebetween with a ratio of area of the nozzle outlet to area of the throat selected to emit the blasting gas from the nozzle outlet to produce a supersonic jet;
a thrust reducer connectable to the nozzle, to receive the supersonic jet exiting the nozzle, the thrust reducer comprising a body with a thrust reducer conduit therethrough, the body being of sufficient length and diameter to cause a flow condition of the jet received from the nozzle outlet to be modified such that a zone of sub-atmospheric pressure forms adjacent a face of the outlet of the nozzle whereby a pressure differential arises between the zone of sub-atmospheric pressure and surrounding atmosphere thereby creating an anti-thrust force in opposition to thrust of the nozzle.
2 . The blast nozzle thrust reduction blasting system of claim 1 , wherein the thrust reducer body includes a coupling portion arranged to connect to a portion of the nozzle adjacent the nozzle outlet and a thrust reduction portion defining the thrust reducer conduit, wherein the thrust reduction portion extends from the coupling portion to a thrust reducer outlet of the thrust reducer.
3 . The blast nozzle thrust reduction blasting system of claim 2 , wherein the predetermined pressure range is 80 psi or greater.
4 . The blast nozzle thrust reduction blasting system of claim 3 , wherein the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.63±5%.
5 . The blast nozzle thrust reduction blasting system of claim 4 , wherein:
the nozzle comprises a # 3 nozzle and the thrust reducer has a thrust reducer outlet diameter of 11.75±2.5% mm and a thrust reduction portion length of 37.50±5% mm; or the nozzle comprises a #4 nozzle and the thrust reducer has a thrust reducer outlet diameter of 15.67±2.5% mm and a thrust reduction portion length of 50.00±5% mm; or the nozzle comprises a #5 nozzle and the thrust reducer has a thrust reducer outlet diameter of 19.58±2.5% mm and a thrust reduction portion length of 62.50±5% mm; or the nozzle comprises a #6 nozzle and the thrust reducer has a thrust reducer outlet diameter of 23.50±2.5% mm and a thrust reduction portion length of 75.00±5% mm; or the nozzle comprises a #7 nozzle and the thrust reducer has a thrust reducer outlet diameter of 27.1±2.5% mm and a thrust reduction portion length of 87.50±5% mm; or the nozzle comprises a #8 nozzle and the thrust reducer has a thrust reducer outlet diameter of 31.33±2.5% mm and a thrust reduction portion length of 100±5% mm; or the nozzle comprises a #10 nozzle and the thrust reducer has a thrust reducer outlet diameter of 39.16±2.5% mm and a thrust reduction portion length of 125±5% mm.
6 - 11 . (canceled)
12 . The blast nozzle thrust reduction blasting system of claim 3 , wherein the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.63±5%, and wherein the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
Nozzle
Thrust reduction
Outlet
Size
portion length (mm)
Diameter (mm)
No. 3
67.5
13.5
No. 4
90.0
18.0
No. 5
112.5
22.5
No. 6
135.0
27.1
No. 7
157.5
31.5
No. 8
179.5
36.0
No. 10
224.5
45.0;
or
wherein the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
Nozzle
Thrust reduction
Outlet Diameter
Size
portion length (mm)
(mm)
No. 3
17.5
10.0
No. 4
23.0
13.0
No. 5
29.0
16.5
No. 6
34.5
20.0
No. 7
40.5
23.0
No. 8
46.0
26.5
No. 10
57.5
33.0;
or
wherein the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.42±5%, and wherein the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
Nozzle
Outlet
Thrust reduction
Size
Diameter (mm)
portion length (mm)
No. 3
10.95
18.0
No. 4
14.60
24.0
No. 5
18.26
30.0
No. 6
21.91
36.0
No. 7
25.56
42.0
No. 8
29.21
48.0
No. 10
36.51
60.0;
or
wherein the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 2.1±5%, and wherein the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
Nozzle
Outlet
Thrust reduction
Size
Diameter (mm)
portion length (mm)
No. 3
13.32
78.5
No. 4
17.76
104.5
No. 5
22.20
130.5
No. 6
26.64
157.0
No. 7
31.08
183.0
No. 8
35.52
209.0
No. 10
44.40
261.0.
13 - 17 . (canceled)
18 . The blast nozzle thrust reduction blasting system of claim 2 , wherein the predetermined pressure range is 80 psi or greater and the nozzle has an A/A* area ratio of 1.63±5%, and wherein the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length ranging between the preferred length and the minimum length for effective thrust reduction as set out in the following table for the nozzle size:
Preferred
Preferred
Minimum Length for
Nozzle
Diameter
Length
effective thrust
Size
mm
mm
reduction (mm)
No. 3
11.8
37.5
23.5
No. 4
15.7
50.0
31.0
No. 5
19.6
62.5
39.0
No. 6
23.5
75.0
46.5
No. 7
27.4
87.5
54.5
No. 8
31.3
100.0
62.0
No. 10
39.2
125.0
77.5.
19 . The blast nozzle thrust reduction blasting system of claim 2 , wherein the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein:
the nozzle comprises a #3 nozzle and herein the length of the thrust reducer is between 7.5 mm and 67.5 mm and the diameter of the thrust reducer is between 10.00 mm and 13.5 mm; or
the nozzle comprises a #4 nozzle and the length of the thrust reducer is between 10.0 mm and 90 mm and the diameter of the thrust reducer is between 13 mm and 18 mm; or
the nozzle comprises a #5 nozzle and the length of the thrust reducer is between 12.5 mm and 112.5 mm and the diameter of the thrust reducer is between 12.5 mm and 22.5 mm; or
the nozzle comprises a #6 nozzle and the length of the thrust reducer is between 15 mm and 135.0 mm and the diameter of the thrust reducer is between 20 mm and 27.1 mm; or
the nozzle comprises a #7 nozzle and the length of the thrust reducer is between 17.5 mm and 157.5 mm and the diameter of the thrust reducer is between 23 mm and 31.5 mm; or
the nozzle comprises a #8 nozzle and the length of the thrust reducer is between 20.0 mm and 179.5 mm and the diameter of the thrust reducer is between 26.5 mm and 36.0 mm; or
the nozzle comprises a #10 nozzle and the length of the thrust reducer is between 25 mm and 224.5 mm and the diameter of the thrust reducer is between 33.0 mm and 45.0 mm.
20 - 26 . (canceled)
27 . The blast nozzle thrust reduction blasting system of claim 1 , wherein the thrust reducer body includes an inlet body portion that is removably received within the thrust reducer conduit of the thrust reducer body.
28 . The blast nozzle thrust reduction blasting system of claim 27 , wherein the inlet body portion comprises a removable sleeve that is removably received within the body.
29 . A method for reducing blast nozzle thrust of a blast nozzle, the method comprising:
providing a blast nozzle including a nozzle body with a nozzle conduit extending from a nozzle inlet to a nozzle outlet with a throat of the conduit therebetween, a ratio of outlet area to throat area constraining the nozzle to produce a supersonic jet; connecting a source of blasting gas sufficient to produce a supersonic jet at the nozzle outlet; and coupling a thrust reducer to an outlet end of the nozzle, the thrust reducer comprising a body with a thrust reducer conduit therethrough, the body being of sufficient length and diameter to cause a flow condition of the jet received from the nozzle outlet to be modified such that a zone of sub-atmospheric pressure forms adjacent a face of the outlet of the nozzle whereby a pressure differential arises between the zone of sub-atmospheric pressure and surrounding atmosphere thereby creating an anti-thrust force in opposition to thrust of the nozzle.
30 - 56 . (canceled)
57 . A thrust reducer arranged to connect to and reduce operational thrust of a blast nozzle, the blast nozzle comprising a body with a conduit therethrough extending from a nozzle inlet for connection to a source of blasting gas and a nozzle outlet for emitting a jet, the nozzle conduit including a throat between the nozzle inlet and the nozzle outlet, the nozzle outlet having a nozzle outlet area and the throat having a throat area, a ratio of the nozzle outlet area to the throat area constraining the nozzle to produce a supersonic jet,
the thrust reducer comprising a body with a thrust reducer conduit therethrough, the body being of sufficient length and diameter to cause a flow condition of the jet received from the nozzle outlet to be modified such that a zone of sub-atmospheric pressure forms adjacent a face of the outlet of the nozzle whereby a pressure differential arises between the zone of sub-atmospheric pressure and surrounding atmosphere thereby creating an anti-thrust force in opposition to thrust of the nozzle.
58 . The thrust reducer of claim 57 , wherein the thrust reducer body includes a coupling portion arranged to connect to a portion of the nozzle adjacent the nozzle outlet and a thrust reduction portion defining the thrust reducer conduit, wherein the thrust reduction portion extends from the coupling portion to a thrust reducer outlet of the thrust reducer.
59 . The thrust reducer of claim 58 , wherein the predetermined pressure range is 80 psi or greater.
60 . The thrust reducer of claim 59 , wherein the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.63±5%.
61 . The thrust reducer of claim 60 , wherein:
the nozzle comprises a #3 nozzle and the thrust reducer has a thrust reducer outlet diameter of 11.75±2.5% mm and a thrust reduction portion length of 37.50±5% mm; or the nozzle comprises a #4 nozzle and the thrust reducer has a thrust reducer outlet diameter of 15.67±2.5% mm and a thrust reduction portion length of 50.00±5% mm; or the nozzle comprises a #5 nozzle and the thrust reducer has a thrust reducer outlet diameter of 19.58±2.5% mm and a thrust reduction portion length of 62.50±5% mm; or the nozzle comprises a #6 nozzle and the thrust reducer has a thrust reducer outlet diameter of 23.50 ±2.5% mm and a thrust reduction portion length of 75.00±5% mm; or the nozzle comprises a #7 nozzle and the thrust reducer has a thrust reducer outlet diameter of 27.1±2.5% mm and a thrust reduction portion length of 87.50±5% mm; or the nozzle comprises a #8 and the thrust reducer has a thrust reducer outlet diameter of 31.33±2.5% mm and a thrust reduction portion length of 100±5% mm; or the nozzle comprises a #10 nozzle and the thrust reducer has a thrust reducer outlet diameter of 39.16±2.5% mm and a thrust reduction portion length of 125±5% mm.
62 - 67 . (canceled)
68 . The thrust reducer of claim 59 , wherein the nozzle has a nozzle exit area to throat area ratio (A/A*) of 1.63±5%, and wherein:
the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
Nozzle
Thrust reduction
Outlet
Size
portion length (mm)
Diameter (mm)
No. 3
67.5
13.5
No. 4
90.0
18.0
No. 5
112.5
22.5
No. 6
135.0
27.1
No. 7
157.5
31.5
No. 8
179.5
36.0
No. 10
224.5
45.0;
or
the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
Nozzle
Thrust reduction
Outlet
Size
portion length (mm)
Diameter (mm)
No. 3
17.5
10.0
No. 4
23.0
13.0
No. 5
29.0
16.5
No. 6
34.5
20.0
No. 7
40.5
23.0
No. 8
46.0
26.5
No. 10
57.5
33.0.
69 . (canceled)
70 . The thrust reducer of claim 59 , wherein the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.42±5%.
71 . The thrust reducer of claim 70 , wherein the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
Outlet
Thrust reduction
Nozzle
Diameter
portion length
Size
(mm)
(mm)
No. 3
10.95
18.0
No. 4
14.60
24.0
No. 5
18.26
30.0
No. 6
21.91
36.0
No. 7
25.56
42.0
No. 8
29.21
48.0
No. 10
36.51
60.0.
72 . The thrust reducer of claim 59 , wherein the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 2.1±5%.
73 . The thrust reducer of claim 72 , wherein the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
Outlet
Thrust reduction
Nozzle
Diameter
portion length
Size
(mm)
(mm)
No. 3
13.32
78.5
No. 4
17.76
104.5
No. 5
22.20
130.5
No. 6
26.64
157.0
No. 7
31.08
183.0
No. 8
35.52
209.0
No. 10
44.40
261.0.
74 . The thrust reducer of claim 58 , wherein the predetermined pressure range is 80 psi or greater and the nozzle has an A/A* area ratio of 1.63±5% and wherein the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length ranging between the preferred length and the minimum length for effective thrust reduction as set out in the following table for the nozzle size:
Preferred
Preferred
Minimum Length for
Nozzle
Diameter
Length
effective thrust
Size
(mm)
(mm)
reduction (mm)
No. 3
11.8
37.5
23.5
No. 4
15.7
50.0
31.0
No. 5
19.6
62.5
39.0
No. 6
23.5
75.0
46.5
No. 7
27.4
87.5
54.5
No. 8
31.3
100.0
62.0
No. 10
39.2
125.0
77.5.
75 . The thrust reducer of claim 58 , wherein the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% and wherein:
the nozzle comprises a #3 nozzle and wherein the length of the thrust reducer is between 7.5 mm and 67.5 mm and the diameter of the thrust reducer is between 10.00 mm and 13.5 mm; or
the nozzle comprises a #4 nozzle and the length of the thrust reducer is between 10.0 mm and 90 mm and the diameter of the thrust reducer is between 13 mm and 18 mm; or
the nozzle comprises a #5 nozzle and the length of the thrust reducer is between 12.5 mm and 112.5 mm and the diameter of the thrust reducer is between 12.5 mm and 22.5 mm; or
the nozzle comprises a #6 nozzle and the length of the thrust reducer is between 15 mm and 135.0 mm and the diameter of the thrust reducer is between 20 mm and 27.1 mm; or
the nozzle comprises a #7 nozzle and the length of the thrust reducer is between 17.5 mm and 157.5 mm and the diameter of the thrust reducer is between 23 mm and 31.5 mm; or the nozzle comprises a # 8 nozzle and the length of the thrust reducer is between 20 . 0 mm and 179 . 5 mm and the diameter of the thrust reducer is between 26 . 5 mm and 36 . 0 mm; or the nozzle comprises a # 10 nozzle and the length of the thrust reducer is between 25 mm and 224 . 5 mm and the diameter of the thrust reducer is between 33 . 0 mm and 45 . 0 mm. Claims 76 - 82 . (Canceled).
83 . The thrust reducer of claim 57 , wherein the thrust reducer body includes an inlet body portion that is removably received within the thrust reducer conduit of the thrust reducer body.
84 . The thrust reducer of claim 83 , wherein the inlet body portion comprises a removable sleeve that is removably received within the body.
85 . The thrust reducer of claim 59 , wherein the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein:
the nozzle comprises a #3 nozzle and the thrust reducer has a thrust reducer outlet diameter of between 10 mm and 13.6 mm and a minimum thrust reduction portion length of between 7.5 mm and 78.5 mm; or the nozzle comprises a #4 nozzle and the thrust reducer has a thrust reducer outlet diameter of between 12.4 mm and 18.1 mm and a minimum thrust reduction portion length of between 10 mm and 104 mm; or the nozzle comprises a #5 nozzle and the thrust reducer has a thrust reducer outlet diameter of between 15.5 mm and 22.6 mm and a minimum thrust reduction portion length of between 12.5 mm and 130.5 mm; or the nozzle comprises a #6 nozzle and the thrust reducer has a thrust reducer outlet diameter of between 18.5 mm and 27.1 mm and a minimum thrust reduction portion length of between 15 mm and 157 mm; or wherein the nozzle comprises a #7 nozzle and the thrust reducer has a thrust reducer outlet diameter of between 21.7 mm and 31.6 mm and a minimum thrust reduction portion length of between 17.5 mm and 183 mm; or the nozzle comprises a #8 nozzle and the thrust reducer has a thrust reducer outlet diameter of between 24.8 mm and 36.1 mm and a minimum thrust reduction portion length of between 20 mm and 209 mm; or the nozzle comprises a #10 nozzle and the thrust reducer has a thrust reducer outlet diameter of between 31 mm and 45.2 mm and a minimum thrust reduction portion length of between 25 mm and 261 mm.
86 - 91 . (canceled)Cited by (0)
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